FFEccLinOrb:

--------------------------------------------------------------------------
   Compute the continous A,B matrices for linearized relative motion in an
   eccentric reference orbit. Discretizes with a zero-order hold if dT provided.

   xDot = a*x + b*u 

   Since version 7.
--------------------------------------------------------------------------
   Form:
   [a,b] = FFEccLinOrb( n, nu, e, dT );
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   n                (1)   Mean orbit rate [rad/s]
   nu               (1)   True anomaly [rad]
   e                (1)   Eccentricity
   dT               (1)   Time-step for discretization (optional)

   -------
   Outputs
   -------
   a               (6,6)  Plant matrix
   b               (6,3)  Input matrix

--------------------------------------------------------------------------
   References: Inalhan, Tillerson, How, "Relative Dynamics and Control of
   Spacecraft Formations in Eccentric Orbits", Journal of Guidance,
   Control & Dynamics, Vol.25, No.1, Jan-Feb 2002.
--------------------------------------------------------------------------
	  Copyright 2004 Princeton Satellite Systems, Inc.
   All rights reserved.
--------------------------------------------------------------------------

Children:

Common: Control/C2DZOH
FormationFlying: Utility/NuDot